Variable angle-of-attack profile entry guidance for a crewed lifting body

Zachary R Putnam, Michael J. Grant, Jenny R. Kelly, Robert D. Braun, Zachary C. Krevor

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

The feasibility of flying a crewed lifting body, such as the HL-20, during entry fromlow-Earth orbit without steady-state body flap deflections was evaluated. This entry strategy mitigates the severity of the aerothermal environment on the vehicle's body flaps and reserves control power for transient maneuvers. A numeric predictor-corrector entry guidance algorithm was developed to accommodate the range of vehicle trim angle-of-attack profiles possible when steady-state body flap deflections are prohibited. Results show that the guidance algorithm is capable of steering the vehicle to a desired target from low-Earth orbit while satisfying a reasonable suite of trajectory constraints, including limits on peak heat rate, peak sensed deceleration, and integrated heat load. Uncertainty analyses confirm this result and show that the vehicle maintains significant performance robustness to expected day-of-flight uncertainties. Additionally, parametric scans over mission design parameters of interest indicate a high level of flexibility is available for the low-Earth orbit return mission. Together, these results indicated that the proposed entry strategy is feasible: crewed lifting bodies may be effectively flown without steady-state body flap deflections.

Original languageEnglish (US)
Title of host publication51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
StatePublished - Aug 19 2013
Externally publishedYes
Event51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 - Grapevine, TX, United States
Duration: Jan 7 2013Jan 10 2013

Publication series

Name51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

Other

Other51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
CountryUnited States
CityGrapevine, TX
Period1/7/131/10/13

Fingerprint

lifting bodies
angle of attack
Angle of attack
vehicles
entry
deflection
Orbits
Earth (planet)
low Earth orbits
profiles
flight
heat
Earth orbits
Deceleration
maneuvers
deceleration
Thermal load
Power control
flexibility
trajectory

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Putnam, Z. R., Grant, M. J., Kelly, J. R., Braun, R. D., & Krevor, Z. C. (2013). Variable angle-of-attack profile entry guidance for a crewed lifting body. In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 (51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013).

Variable angle-of-attack profile entry guidance for a crewed lifting body. / Putnam, Zachary R; Grant, Michael J.; Kelly, Jenny R.; Braun, Robert D.; Krevor, Zachary C.

51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 2013. (51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Putnam, ZR, Grant, MJ, Kelly, JR, Braun, RD & Krevor, ZC 2013, Variable angle-of-attack profile entry guidance for a crewed lifting body. in 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013, 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013, Grapevine, TX, United States, 1/7/13.
Putnam ZR, Grant MJ, Kelly JR, Braun RD, Krevor ZC. Variable angle-of-attack profile entry guidance for a crewed lifting body. In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 2013. (51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013).
Putnam, Zachary R ; Grant, Michael J. ; Kelly, Jenny R. ; Braun, Robert D. ; Krevor, Zachary C. / Variable angle-of-attack profile entry guidance for a crewed lifting body. 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013. 2013. (51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013).
@inproceedings{f661fdbc1b504003ab2ee095faba894a,
title = "Variable angle-of-attack profile entry guidance for a crewed lifting body",
abstract = "The feasibility of flying a crewed lifting body, such as the HL-20, during entry fromlow-Earth orbit without steady-state body flap deflections was evaluated. This entry strategy mitigates the severity of the aerothermal environment on the vehicle's body flaps and reserves control power for transient maneuvers. A numeric predictor-corrector entry guidance algorithm was developed to accommodate the range of vehicle trim angle-of-attack profiles possible when steady-state body flap deflections are prohibited. Results show that the guidance algorithm is capable of steering the vehicle to a desired target from low-Earth orbit while satisfying a reasonable suite of trajectory constraints, including limits on peak heat rate, peak sensed deceleration, and integrated heat load. Uncertainty analyses confirm this result and show that the vehicle maintains significant performance robustness to expected day-of-flight uncertainties. Additionally, parametric scans over mission design parameters of interest indicate a high level of flexibility is available for the low-Earth orbit return mission. Together, these results indicated that the proposed entry strategy is feasible: crewed lifting bodies may be effectively flown without steady-state body flap deflections.",
author = "Putnam, {Zachary R} and Grant, {Michael J.} and Kelly, {Jenny R.} and Braun, {Robert D.} and Krevor, {Zachary C.}",
year = "2013",
month = "8",
day = "19",
language = "English (US)",
isbn = "9781624101816",
series = "51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013",
booktitle = "51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013",

}

TY - GEN

T1 - Variable angle-of-attack profile entry guidance for a crewed lifting body

AU - Putnam, Zachary R

AU - Grant, Michael J.

AU - Kelly, Jenny R.

AU - Braun, Robert D.

AU - Krevor, Zachary C.

PY - 2013/8/19

Y1 - 2013/8/19

N2 - The feasibility of flying a crewed lifting body, such as the HL-20, during entry fromlow-Earth orbit without steady-state body flap deflections was evaluated. This entry strategy mitigates the severity of the aerothermal environment on the vehicle's body flaps and reserves control power for transient maneuvers. A numeric predictor-corrector entry guidance algorithm was developed to accommodate the range of vehicle trim angle-of-attack profiles possible when steady-state body flap deflections are prohibited. Results show that the guidance algorithm is capable of steering the vehicle to a desired target from low-Earth orbit while satisfying a reasonable suite of trajectory constraints, including limits on peak heat rate, peak sensed deceleration, and integrated heat load. Uncertainty analyses confirm this result and show that the vehicle maintains significant performance robustness to expected day-of-flight uncertainties. Additionally, parametric scans over mission design parameters of interest indicate a high level of flexibility is available for the low-Earth orbit return mission. Together, these results indicated that the proposed entry strategy is feasible: crewed lifting bodies may be effectively flown without steady-state body flap deflections.

AB - The feasibility of flying a crewed lifting body, such as the HL-20, during entry fromlow-Earth orbit without steady-state body flap deflections was evaluated. This entry strategy mitigates the severity of the aerothermal environment on the vehicle's body flaps and reserves control power for transient maneuvers. A numeric predictor-corrector entry guidance algorithm was developed to accommodate the range of vehicle trim angle-of-attack profiles possible when steady-state body flap deflections are prohibited. Results show that the guidance algorithm is capable of steering the vehicle to a desired target from low-Earth orbit while satisfying a reasonable suite of trajectory constraints, including limits on peak heat rate, peak sensed deceleration, and integrated heat load. Uncertainty analyses confirm this result and show that the vehicle maintains significant performance robustness to expected day-of-flight uncertainties. Additionally, parametric scans over mission design parameters of interest indicate a high level of flexibility is available for the low-Earth orbit return mission. Together, these results indicated that the proposed entry strategy is feasible: crewed lifting bodies may be effectively flown without steady-state body flap deflections.

UR - http://www.scopus.com/inward/record.url?scp=84881400042&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84881400042&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84881400042

SN - 9781624101816

T3 - 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

BT - 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

ER -